Abstract
Numerical methods have been developed to analyse incompressible viscous flows past three dimensional wings with deflected flap using viscous-inviscid interaction techniques. By using a surface transpiration technique, a panel method for external potential flow calculation is combined with a boundary-layer calculation based on an integral method. For the clean wing case, both three dimensional boundary layer corrections and two dimensional boundary layer corrections are applied in a strip theory sense and compared with experimental results in the literature. It is found that for wings with moderate aspect ratio and sweep angle, viscous corrections at low incidences by the two methods are of the same order. Based on this observation, a two dimensional boundary layer correction method (strip theory sense), including the wake-boundary layer interaction, is developed for the case of wings with a deflected flap of similar planform. Experiments have been conducted to assess the accuracy of the calculation methods for wings with deflected flap; comparison between the experimental and predicted results is encouraging.
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